Methods for operating gas turbine engines
AssigneeGeneral Electric Company
InventorIvan Elmer Woltmann
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Abstract
A combustion control system controls a turbine engine that includes a fuel manifold and a plurality of fuel injectors. The control system includes a fuel pulsator and a controller. The fuel pulsator is coupled in flow communication with the plurality of injectors and the fuel manifold. The controller is coupled to the fuel pulsator such that the pulsator is between the controller and the fuel manifold. The controller is variably selectable and configured to facilitate promoting stable combustion.
Claims5
A method for controlling an aircraft engine including a combustor, a fuel manifold, and a plurality of fuel injectors, the fuel manifold in flow communication with the fuel injectors for supplying fuel to the combustor, the combustor defining a combustion chamber, said method comprising:
- supplying fuel to the combustor fuel injectors through a fuel pulsator and the fuel manifold, wherein the fuel pulsator is coupled to a controller;
- and
- variably operating the controller without continuous feedback to pulse fuel with the fuel pulsator to facilitate promoting stable combustion within the combustion chamber.
Dependencies are inferred from the claim text.